CN215690732U

CN215690732U - Turbine device and breathing machine

Info

Publication number: CN215690732U
Application number: CN202121467184.4U
Authority: CN
Inventors: 李增; 古剑仁
Original assignee: Shenzhen Prunus Medical Co Ltd
Current assignee: Shenzhen Prunus Medical Co Ltd
Priority date: 2021-06-30
Filing date: 2021-06-30
Publication date: 2022-02-01
Anticipated expiration: 2031-06-30

Abstract

The utility model provides a turbine device and breathing machine, wherein, turbine device includes the turbine box, non-contact arranges the turbine subassembly in the turbine box and overlaps in the flexible buffering subassembly of predetermineeing the position of turbine subassembly, one side that flexible buffering subassembly deviates from the turbine subassembly leans on and/or is fixed with the inner wall of turbine box to support and be fixed in the turbine box with the turbine subassembly. Because the flexible buffer component is arranged between the turbine component and the turbine box in a sleeved mode, the turbine component and the turbine box can be prevented from being in direct contact in all directions, the turbine component can be supported and fixed, and the flexible buffer component can be used for fully absorbing vibration energy generated by the turbine component when the turbine component runs, so that mechanical vibration caused by the transmission of the vibration energy to the turbine box and peripheral parts is avoided, and the whole mechanical vibration of the device and the caused noise pollution are effectively reduced.

Description

Turbine device and breathing machine

Technical Field

The utility model relates to the field of medical instruments, in particular to a turbine device and a breathing machine.

Background

In an electric control respirator, a turbine is generally adopted to pressurize gas and directly deliver the gas with certain pressure to a patient, or the pressurized gas is used as a low-pressure gas source of an inhalation valve. The high-speed rotation of the turbine makes the turbine and peripheral devices easily generate mechanical vibration, thereby causing problems such as noise pollution and the like.

SUMMERY OF THE UTILITY MODEL

The utility model mainly solves the technical problem of providing a turbine device and a breathing machine using the turbine device so as to achieve the purpose of reducing mechanical vibration.

According to a first aspect, there is provided in an embodiment a turbine arrangement comprising:

a turbine case;

a turbine assembly arranged non-contactingly within the turbine case; and

the flexible buffer assembly is sleeved at the preset position of the turbine assembly, one side of the flexible buffer assembly, which deviates from the turbine assembly, abuts against and/or is fixed with the inner wall of the turbine box, so that the turbine assembly is supported and fixed in the turbine box.

In one embodiment, the turbine assembly includes a turbine body portion arranged in a turbine case in a first direction without contact; the flexible buffer assembly comprises a flexible buffer ring which is sleeved on the turbine main body part and is abutted against and/or fixed with the inner wall of the turbine box so as to support and fix the turbine main body part.

In one embodiment, the turbine assembly further includes an air outlet end portion formed at one end of the turbine main body portion in the first direction along the second direction, the turbine box is provided with an air outlet, the flexible buffer assembly further includes a flexible buffer sleeve, the flexible buffer sleeve is arranged at the air outlet end portion, and the flexible buffer sleeve is inserted into and fixed in the air outlet to communicate the air outlet end portion with the air outlet.

In one embodiment, the flexible buffer ring comprises a first buffer ring and a second buffer ring, and the first buffer ring and the second buffer ring are sleeved on the turbine main body part at intervals along the first direction.

In one embodiment, the turbine casing has a support structure which is formed by an inner wall of the turbine casing and extends toward the first cushion collar, and a side of the first cushion collar facing away from the turbine main body part abuts against and/or is fixed to the support structure.

In one embodiment, the first buffer collar comprises:

the inner ring part is provided with a first groove structure, the first groove structure is arranged on the surface of the turbine main part in the first direction, and the inner ring part is inserted in the first groove structure in an interference manner; and

and the contact part is clamped between the support structure and the surface of the turbine main body part, and is formed by extending the periphery of the inner ring part along the first direction in a single-sided or double-sided mode.

In one embodiment, the support structure comprises:

the abutting piece is used for abutting against the surface of one side, away from the inner ring part, of the contact part; and

the limiting pieces are distributed on one side of the abutting piece along the first direction, protrude out of the surface of the abutting piece facing one side of the contact part and are used for abutting against the end face of the contact part in the first direction.

In one embodiment, the turbine main body includes a motor portion and a heat dissipation portion provided at an end side of the motor portion in a first direction, the turbine box has a first space, a second space, and a transition through hole communicating the first space and the second space, the motor portion is located in the first space, and the heat dissipation portion is located in the second space; the first buffer ring is sleeved on the motor part, and the second buffer ring is sleeved at one end of the motor part adjacent to the heat dissipation part or between the motor part and the heat dissipation part.

In one embodiment, a second groove structure is formed between the motor part and the heat dissipation part around the first direction, a flange structure extending into the first space and/or the second space along the first direction is formed around the transition through hole, the second buffer ring is inserted into the second groove structure in an interference manner, and one side of the second buffer ring departing from the second groove structure abuts against and is attached to the flange structure.

In one embodiment, the silencer also comprises a silencing cotton component which is arranged along the inner wall of the turbine box and is used for silencing and reducing noise.

According to a second aspect, an embodiment provides a ventilator comprising a housing and a turbine device disposed in the housing, the turbine device employing the turbine device of the first aspect.

According to the turbine device of the embodiment, the turbine device comprises the turbine box, the turbine assembly arranged in the turbine box in a non-contact mode and the flexible buffering assembly sleeved on the preset position of the turbine assembly, and one side, away from the turbine assembly, of the flexible buffering assembly abuts against and/or is fixed to the inner wall of the turbine box so as to support and fix the turbine assembly in the turbine box. Because the flexible buffer component is arranged between the turbine component and the turbine box in a sleeved mode, the turbine component and the turbine box can be prevented from being in direct contact in all directions, the turbine component can be supported and fixed, and the flexible buffer component can be used for fully absorbing vibration energy generated by the turbine component when the turbine component runs, so that mechanical vibration caused by the transmission of the vibration energy to the turbine box and peripheral parts is avoided, and the whole mechanical vibration of the device and the caused noise pollution are effectively reduced.

Drawings

Fig. 1 is an axial sectional structural view of a turbine device according to an embodiment.

Fig. 2 is a partially enlarged schematic view of a region a in fig. 1.

Fig. 3 is a partially enlarged view of the region B in fig. 1.

Fig. 4 is a schematic view illustrating a partial structural assembly of a turbine assembly and a turbine box in the turbine device according to the embodiment.

Fig. 5 is an exploded view of a turbine assembly and a turbine box of the turbine device according to an embodiment.

FIG. 6 is a schematic structural view of a first buffer ring in the turbine device according to an embodiment.

Fig. 7 is an axial sectional structural view of a turbine box in the turbine device according to the embodiment.

Fig. 8 is a schematic circumferential sectional structure view of a turbine box in the turbine device of the embodiment.

In the figure:

10. a turbine case; 10a, a first space; 10b, a second space; 10c, transition through holes; 10d, flange structure; 11. a top shell; 12. a base; 13. an air outlet; 13-1, a first bump structure; 14. an abutting member; 15. a limiting member;

20. a turbine assembly; 21. a motor section; 22. a heat dissipating section; 23. an air inlet end part; 24. an air outlet end part; 24-1, a second bump structure;

30. a flexible cushioning component; 31. a first buffer ring; 31-1, an inner ring portion; 31-2, a contact portion; 32. a second buffer ring; 33. a flexible buffer sleeve; 33-1, a first recessed structure; 33-2 and a second concave structure.

Detailed Description

The present invention will be described in further detail with reference to the following detailed description and accompanying drawings. Wherein like elements in different embodiments are numbered with like associated elements. In the following description, numerous details are set forth in order to provide a better understanding of the present application. However, those skilled in the art will readily recognize that some of the features may be omitted or replaced with other elements, materials, methods in different instances. In some instances, certain operations related to the present application have not been shown or described in detail in order to avoid obscuring the core of the present application from excessive description, and it is not necessary for those skilled in the art to describe these operations in detail, so that they may be fully understood from the description in the specification and the general knowledge in the art.

Furthermore, the features, operations, or characteristics described in the specification may be combined in any suitable manner to form various embodiments. Also, the various steps or actions in the method descriptions may be transposed or transposed in order, as will be apparent to one of ordinary skill in the art. Thus, the various sequences in the specification and drawings are for the purpose of describing certain embodiments only and are not intended to imply a required sequence unless otherwise indicated where such sequence must be followed.

The numbering of the components as such, e.g., "first", "second", etc., is used herein only to distinguish the objects as described, and does not have any sequential or technical meaning. The term "connected" and "coupled" when used in this application, unless otherwise indicated, includes both direct and indirect connections (couplings).

As used herein, the term "first direction" refers to the direction of the overall axial centerline of the turbine assembly when it is in normal placement, assembly use, or operation; in general, it can also be understood that: as for the turbine motor, when the turbine motor is in a cylindrical coordinate system, three orthogonal directions of an axial direction, a circumferential direction and a radial direction can be naturally formed or defined; the first direction is an axial direction of the turbine motor.

The term "second direction" as used herein refers to a direction that is spatially perpendicular to the axis of the turbine assembly as a whole when the turbine assembly is in normal placement, assembly use, or operation; in general, it can also be understood that: the second direction is a tangential direction tangential to the circumferential direction of the turbine motor.

According to the turbine device, the flexible buffer assembly sleeved on the turbine assembly is utilized to establish a flexible contact relation or an indirect connection relation between the turbine assembly and the turbine box, so that the turbine assembly can be placed and fixed in the turbine box in a non-direct contact manner; because the flexible buffer component is arranged between the turbine component and the turbine box in a sleeved mode, the turbine component and the turbine box can be prevented from being in direct contact in an all-round mode, the turbine component can be supported and fixed, and when the turbine component runs, vibration energy generated by the turbine component can be fully absorbed by the flexible buffer component, so that mechanical vibration caused by the transmission of the vibration energy to the turbine box and peripheral parts can be avoided, the whole mechanical vibration and the caused noise of the device can be effectively reduced, and the purposes of shock absorption and noise reduction are achieved.

Example one

Referring to fig. 1 to 8, a turbine device provided in this embodiment can be applied to medical equipment, such as a ventilator, for pressurizing and delivering gas; the turbine device includes a turbine cartridge 10, a turbine assembly 20, and a flexible buffer assembly 30, which are described separately below.

Referring to fig. 1, 4, 7 and 8, the turbine box 10 is mainly used to provide a structural assembly space for the turbine assembly 20 and the like, so that the device is integrally assembled in the respirator through the turbine box 10; generally, the turbine box 10 is formed by two parts, i.e., a top shell 11 and a base 12, which are assembled together, so as to form a structural space capable of accommodating the turbine assembly 20 and other components in the turbine box 10; meanwhile, in order to ensure the normal operation of the turbine assembly 20, an air inlet communicated with an air inlet end of the turbine assembly 20 and an air outlet 13 communicated with an air outlet end of the turbine assembly 20 are generally further provided on the turbine box 10.

Referring to fig. 1, 5 and 6, the turbine assembly 20 mainly serves to pressurize and transport gas such as air, and may be divided into an impeller portion, a motor portion 21, a heat dissipation portion 22 and other portions along a first direction (i.e., an axial direction) according to a structural structure and an operation principle of the turbine assembly 20; the motor part 21 and the heat dissipation part 22 can be regarded as a turbine main body part of the turbine assembly 20, the impeller part generally has an air inlet end and an air outlet end, the air inlet end is generally arranged on one side of the impeller part away from the motor part 21 along the axial direction, and the air inlet end can be defined as an air inlet end part 23; the air outlet end is generally arranged along the tangential direction (i.e. the second direction) of the impeller portion, so that the air outlet end can be defined as an air outlet end portion 24; in the present embodiment, the turbine assembly 20 is disposed and placed in the turbine box 10 in a non-contact manner, which is different from the conventional manner in which the turbine and the box body are directly fixed or connected in a hard contact manner by hardware such as screws.

It is understood that reference to "non-contact" means that the turbine assembly 20 is not in direct contact with any portion (e.g., the inner wall) of the turbine housing 10, but is in indirect contact or indirectly connected through an intermediate member, such that mechanical vibrations induced by operation of the turbine assembly 20 are reduced by selection of materials, configurations, etc. of the intermediate member.

Referring to fig. 1 to 6, the flexible buffer assembly 30 is mainly used as an intermediate member between the turbine assembly 20 and the turbine box 10, and on one hand, functions to support and fix the turbine assembly 20 in the turbine box 10, and on the other hand, absorbs the vibration energy of the turbine assembly 20 and prevents the vibration energy from being transmitted to the turbine box 10, so as to play roles of energy dissipation, shock absorption and noise reduction. The flexible bumper assembly 30 may be a single structural member or a collection of structural members; the structural member of the flexible buffer assembly 30 adopts a ring-shaped structure or a sleeve-shaped structure, and is sleeved on a preset part of the turbine assembly 20 in a surrounding sleeved manner, such as any one or more of the motor part 21, the heat dissipation part 22, the air inlet end part 23 and the air outlet end part 24; one side of the structural member of the flexible buffer assembly 30, which faces away from the turbine assembly 20 (specifically, the corresponding preset portion), abuts against and/or is fixed to the inner wall of the turbine box 10, so that the turbine assembly 20 is supported and fixed inside the turbine box 10 by the flexible buffer assembly 30; meanwhile, each structural member of the flexible buffer assembly 30 may be made of a flexible material or an elastic material having a certain reversible deformation, such as rubber, silica gel, etc., so as to absorb the vibration energy of the turbine assembly 20 by using the deformation effect thereof, thereby performing the functions of energy dissipation, shock absorption and noise reduction. In specific implementation, the number, structural form and the like of the structural members of the flexible buffer assembly 30 can be specifically selected and set to meet or adapt to actual conditions or requirements of the internal structure of the turbine box 10, the outer contour shape structure of the turbine assembly 20, the direct structural matching relationship between the turbine assembly 20 and the turbine box 10, the installation stability of the turbine assembly 20, the size of a preset part and the like.

It is noted that the person skilled in the art will know that the main difference between the mentioned ring-like and sleeve-like structures is the difference in length or width of the structural members in the axial direction; typically, the length of the sleeve-like structure in the axial direction is significantly greater than the loop-like structure.

In one embodiment, referring to fig. 1, 4 and 5, the flexible buffer assembly 30 includes a flexible buffer ring in a ring-shaped structure, the flexible buffer ring is disposed on the turbine main body, and a side of the flexible buffer ring facing away from the turbine main body abuts against and/or is fixed to an inner wall of the turbine box 10; because the overall center of gravity of the turbine assembly 20 is located at the turbine main body part, and the turbine main body part occupies the largest proportion in the structural framework of the turbine assembly 20, the flexible buffer ring is utilized to support and fix the turbine main body part in a sleeved manner, so that the turbine assembly 20 can be ensured to be stably placed in the turbine box 10. In specific implementation, the flexible buffer ring may be one, for example, by increasing the length dimension of the flexible buffer ring in the axial direction, the flexible buffer ring may be sleeved in the middle of the turbine main body portion to distinguish or can ensure that the turbine assembly 20 maintains an axially balanced position, so as to stably support and fix the turbine assembly 20. Of course, the number of the flexible buffer rings may also be multiple, the multiple flexible buffer rings include a first buffer ring 31 and a second buffer ring 32, the first buffer ring 31 and the second buffer ring 32 are arranged at intervals along the first direction, and are respectively sleeved on the turbine main body part, so as to form a two-position or multi-position structural supporting and fixing effect on the turbine assembly 20; specifically, the first buffer ring 31 and the second buffer ring 32 may be respectively located at two ends of the turbine main body in the first direction, for example, the first buffer ring 31 is located at a position where the motor portion 21 is connected to the impeller portion, and the second buffer ring 32 is located at a position where the motor portion 21 is connected to the heat dissipation portion 22.

It will be understood by those skilled in the art that the first buffer ring 31 and the second buffer ring 32 each do not only refer to one buffer ring, but they may also each refer to a set of buffer rings consisting of a plurality of buffer rings, i.e. the "first" and "second" here refer not only to a grouping of buffer rings, but also to the number thereof.

In one embodiment, referring to fig. 1, 3, 4 and 5, the flexible buffer assembly 30 further includes a flexible buffer sleeve 33 having a sleeve-shaped structure; generally, since the air outlet end 24 of the turbine assembly 20 needs to be butted with the air outlet 13 of the turbine box 10 so as to exhaust or deliver the pressurized air; therefore, the flexible buffer sleeve 33 can be used as a connecting medium between the air outlet end portion 24 and the air outlet 23; specifically, the air outlet end 24 is partially inserted into the air outlet 13, one end of the flexible buffer sleeve 33 is sleeved on the air outlet end 24, and the other end is inserted into and fixed (e.g., bonded) to the air outlet 13; thus, the flexible buffer sleeve 33 can be used to establish a communication relationship between the air outlet end portion 24 and the air outlet 13 so as to avoid hard contact or direct contact between the two, and can also play a role in limiting the turbine assembly 20 from moving laterally along the axial direction so as to assist the flexible buffer ring to ensure that the turbine assembly 20 is stably assembled in the turbine box 10.

In one embodiment, referring to fig. 1, 3, 4, 5 and 7, the air outlet 13 is a tubular structure protruding from an outer surface of the turbine box 10 (e.g., the base 12), and a first protruding structure 13-1 is disposed on an inner circumferential surface of the air outlet 13; correspondingly, the first concave structure 33-1 is arranged on the outer peripheral surface of the flexible buffer sleeve 33, and after the flexible buffer sleeve 33 is inserted into the air outlet 13, the first convex structure 13-1 can be inserted into the first concave structure 33-1, so that the flexible buffer sleeve 33 can be further ensured to be firmly fixed with the air outlet 13; meanwhile, a second bulge structure 24-1 is arranged on the outer peripheral surface of the air outlet end portion 24; correspondingly, the inner circumferential surface of the flexible buffer sleeve 33 is provided with a second concave structure 33-2, and when the flexible buffer sleeve 33 is sleeved on the air outlet end portion 33, the second convex structure 24-1 can be embedded in the second concave structure 33-2, so that the flexible buffer sleeve 33 can be stably sleeved on the air outlet end portion 24; based on this, through the structural optimization to air-out tip 24, flexible cushion sleeve 33 and air outlet 13, both can avoid air-out tip 24 and air outlet 13 direct contact to play energy-absorbing shock-absorbing effect, can avoid again that flexible cushion sleeve 33 accident drops.

In one embodiment, referring to fig. 1, fig. 2, fig. 4, fig. 5, fig. 7 and fig. 8, a support structure is disposed in the turbine box 10, and is mainly used for supporting and fixing the turbine assembly 20 in cooperation with the flexible buffer ring, and preventing a local area of the contour surface of the turbine assembly 20 from directly contacting the inner wall of the turbine box 10 when the flexible buffer ring is structurally deformed; specifically, the support structure is mainly used for cooperating with the first buffer ring 31, and may be formed by extending the inner wall of the turbine box 10 toward the first buffer ring 31, or may be a structural member independently installed on the inner wall side of the turbine box 10; and the supporting structure may be one or more, for example, the supporting structure is formed by respectively extending from one or more specific positions of the inner walls of the top shell 11 and the bottom shell 12; the key points are as follows: the distance between the surface of the support structure facing the first buffer ring 31 and the inner wall of the turbine box 10 (which can also be understood as the setting height of the support structure relative to the inner wall of the turbine box 10) is larger than the distance between any position of the contour surface of the turbine assembly 20 and the inner wall of the turbine box 10, and the support structure should be at least located on two opposite sides of the circumference direction of the turbine assembly 20 to be capable of approximately clamping the turbine assembly 20; therefore, when the first buffer ring 31 is sleeved on the turbine main body part and one side of the first buffer ring, which is far away from the turbine main body part, abuts against and/or is fixed on the supporting structure, a sufficient structural gap can be ensured between the turbine assembly 20 (particularly the turbine main body part) and the inner wall of the turbine box 10, and hard contact or direct contact between the turbine assembly 20 and the inner wall of the turbine box 10 is avoided; meanwhile, the existence of the supporting structure can also provide structural guarantee for the turbine assembly 20 to be stably supported and fixed in the turbine box 10.

In one embodiment, referring to fig. 1, 2 and 6, the first cushion ring 31 includes an inner ring portion 31-1 and a contact portion 31-2 that are coaxially disposed inside and outside, the contact portion 31-2 is formed by extending the outer circumference of the inner ring portion 31-1 along a first direction (or axial direction) in a single-sided or double-sided manner, so that the overall axial cross-sectional shape of the first cushion ring 31 is similar to an "L" or "T" shape; the inner ring portion 31-1 is mainly used for structural combination with a turbine main body portion, a first groove structure (not labeled in the figure) is arranged on the surface of the turbine main body portion around a first direction (or along a circumferential direction), and the first groove structure can be located on the surface of the motor portion 21, for example, a ring groove structure is arranged on the surface of the motor portion 21 to form the first groove structure; the first groove structure may also be located between the motor part 21 and the impeller part, for example, after the two parts are combined, a ring groove structure is naturally formed or constructed between the two parts to serve as the first groove structure; the inner ring part 31-1 is inserted in the first ring groove structure in an interference manner so as to realize firm combination with the turbine main body part; the contact portion 31-2 is in abutting contact and/or fixed with the support structure so as to be able to closely follow the contour surface of the turbine main body while being clamped between the support structure and the surface of the turbine main body, thereby avoiding direct or hard contact of the turbine assembly 20 with the turbine case 10 or the support structure.

In one embodiment, referring to fig. 1, fig. 2, fig. 4, fig. 5, fig. 7 and fig. 8, the supporting structure includes an abutting member 14 and a limiting member 15; wherein, the limiting members 15 are distributed on one side of the abutting member 14 along the first direction and are arranged to protrude from the surface of the abutting member 14 facing to one side of the contact portion 31-2, so that the whole of each supporting structure presents an approximately step-shaped structure; when the first cushion ring 31 is combined with the support structure, a surface of the contact portion 31-2 on a side facing away from the inner ring portion 31-1 (which may be understood as an outer circumferential surface of the first cushion ring 31) abuts against the contact abutment 14, and a part of an end surface of the contact portion 31-2 in the first direction (which may be understood as an axial end surface of the first cushion ring 31) abuts against the stopper 15 by self-contact; therefore, the first buffer ring 31 can be stably clamped and fixed on the turbine main body part by using the supporting structure, and the turbine main body part or the turbine assembly 20 can be prevented from generating unilateral deviation along the axial direction, so that the effect of stabilizing the assembling position of the turbine assembly 20 is achieved.

In one embodiment, referring to fig. 7 in combination with fig. 1, by dividing or dividing the inner space of the turbine box 10, the turbine box 10 has a first space 10a and a second space 10b distributed along a first direction, the first space 10a is relatively closed, the second space 10b can be communicated with the outer space of the turbine box 10, and the first space 10a and the second space 10b are communicated through a transition through hole 10 c; the motor part 21 and the impeller part (including the air inlet end part 23 and the air outlet end part 24) are both positioned in the first space 10a, and the heat dissipation part 22 is positioned in the second space 10b, so that the heat generated by the motor part 21 can be dissipated to the external space through the heat dissipation part 22; meanwhile, based on the spatial structure of the turbine box 10, the first buffer ring 31 may be disposed at one end of the motor portion 21 adjacent to the impeller portion (e.g., a portion where the motor portion 21 is joined to the impeller portion), and the second buffer ring 32 may be disposed at one end of the motor portion 21 adjacent to the heat dissipation portion 22 (e.g., a portion where the motor portion 21 is joined to the heat dissipation portion 22, specifically, a portion near a position where the transition through hole 10c is located), so that the first buffer ring 31 and the second buffer ring 32 are used to support and fix the motor portion 21 from two axial ends of the motor portion 21, and the stability of the overall assembly of the turbine assembly 20 may be ensured; moreover, the number of potential contact positions between the turbine assembly 20 and the turbine box 10 can be effectively reduced, and favorable conditions are created for optimizing the air duct structure between the turbine box 10 and the turbine assembly 20, reducing the structural complexity inside the device and the like.

In one embodiment, referring to fig. 7 in combination with fig. 1, a second groove structure (not labeled) is formed between the motor portion 21 and the heat dissipation portion 22, and the second groove structure is disposed on the outer circumferential surface of the turbine main body portion around the first direction; meanwhile, a flange structure 10d is provided in the turbine box 10, the flange structure 10d is distributed around the transition through hole 10c and extends into the second space 10b along the first direction (of course, in other embodiments, it may also extend into the first space 10a simultaneously or separately); correspondingly, the second cushion ring 32 is clamped between the flange structure 10d and the turbine main body part, and the inner peripheral side of the second cushion ring is inserted into the second groove structure in an interference manner, and the outer peripheral side of the second cushion ring abuts against and fits with the flange structure 10 d; therefore, through the optimization of the second buffer ring 32 and the peripheral structure thereof, firstly, the second buffer ring 32 can be used for isolating the turbine box 10 from the turbine assembly 20 so as to establish a flexible contact relationship between the two, and the first buffer ring 32 (and the flexible buffer sleeve 33) is matched to realize the support and fixation of the turbine assembly 20; secondly, a sealing effect can be formed between the first space 10a and the second space 10b, so that the motor part 21 can be accommodated in a relatively closed structural space, and favorable structural conditions are created for enhancing the heat dissipation effect of the turbine assembly 20 and the pressurization effect of gas; thirdly, on the premise that the supporting structure is formed by the abutting part 14 and the limiting part 15, the second buffer ring 32 is clamped and fixed by the flange structure 10d and the turbine assembly 20 in the radial direction, so that the turbine assembly 20 can be prevented from shifting in the axial direction, and conditions are created for quick assembly and disassembly of the turbine assembly 20.

In other embodiments, the second buffer ring 32 and the flange structure 10d may also be structurally configured with reference to the first buffer ring 31 and the support structure, respectively, and the two sets of structures are opposite to each other along the axial direction, so as to form the position-limiting members 15 oppositely arranged at two ends of the turbine assembly 20, and the position-limiting function of the position-limiting members 15 can be utilized to provide structural support for stably supporting the turbine assembly 20 and preventing the turbine assembly from axial deviation.

The turbine device provided by an embodiment further includes a noise reduction cotton assembly (not shown in the figure), which may be a collection of a plurality of noise reduction cotton blocks, each noise reduction cotton block is attached to one or more region parts of the inner wall of the turbine box 10, such as a structural gap between the turbine assembly 20 and the turbine box 10, according to the internal structure of the turbine box 10; the sound attenuation cotton component is equivalent to a sound attenuation material layer formed in the turbine box 10, so that good sound attenuation and noise reduction effects can be achieved.

Example two

The second embodiment provides a ventilator, which comprises a casing and a turbine device; with reference to fig. 1 to 8, the turbine device according to the foregoing embodiment is used, and in particular, the turbine device may be integrally placed and fixed in a casing, such as detachably, by a turbine box 10. Based on the structural structure and the functional characteristics of the turbine device, the mechanical vibration generated by the turbine device and peripheral devices can be effectively reduced, the integral vibration and noise of the respirator are smaller, and the respirator can be safely and stably operated for a long time.

The present invention has been described in terms of specific examples, which are provided to aid understanding of the utility model and are not intended to be limiting. For a person skilled in the art to which the utility model pertains, several simple deductions, modifications or substitutions may be made according to the idea of the utility model.

Claims

1. A turbine apparatus, comprising:

a turbine case;

a turbine assembly arranged non-contactingly within the turbine case; and

2. The turbine arrangement of claim 1, wherein the turbine assembly comprises a turbine body portion arranged non-contactingly within a turbine box along a first direction; the flexible buffer assembly comprises a flexible buffer ring which is sleeved on the turbine main body part and is abutted against and/or fixed with the inner wall of the turbine box so as to support and fix the turbine main body part.

3. The turbine device according to claim 2, wherein the turbine assembly further includes an air outlet end portion formed at one end of the turbine main body portion in the first direction along the second direction, the turbine box is provided with an air outlet, the flexible buffer assembly further includes a flexible buffer sleeve, the flexible buffer sleeve is disposed at the air outlet end portion, and the flexible buffer sleeve is inserted and fixed in the air outlet to communicate the air outlet end portion with the air outlet.

4. The turbine assembly of claim 2, wherein the flexible buffer ring comprises a first buffer ring and a second buffer ring, and the first buffer ring and the second buffer ring are sleeved on the turbine main body part at intervals along the first direction.

5. The turbine arrangement as claimed in claim 4, characterized in that the turbine housing has a support structure which is formed by an inner wall of the turbine housing and extends towards the first buffer ring, the side of the first buffer ring facing away from the turbine body being in abutment with and/or fixed to the support structure.

6. The turbine assembly of claim 5, wherein the first buffer ring comprises:

7. The turbine assembly of claim 6, wherein the support structure comprises:

8. The turbine device according to claim 4, wherein the turbine main body portion includes a motor portion and a heat dissipation portion provided on an end side of the motor portion in the first direction, the turbine box has a first space, a second space, and a transition through hole that communicates the first space with the second space, the motor portion is located in the first space, and the heat dissipation portion is located in the second space; the first buffer ring is sleeved on the motor part, and the second buffer ring is sleeved at one end of the motor part adjacent to the heat dissipation part or between the motor part and the heat dissipation part.

9. The turbine device according to claim 8, wherein a second groove structure is formed between the motor part and the heat dissipation part around the first direction, a flange structure extending into the first space and/or the second space along the first direction is formed around the transition through hole, the second buffer ring is inserted into the second groove structure in an interference fit manner, and one side of the second buffer ring, which faces away from the second groove structure, abuts against and fits against the flange structure.

10. The turbine assembly of claim 1, further comprising a sound dampening cotton assembly disposed adjacent an inner wall of the turbine housing for sound dampening and noise reduction.

11. A ventilator comprising a housing and a turbine assembly disposed within the housing, the turbine assembly employing the turbine assembly of any one of claims 1-10.